US20120260669A1 - Front centerbody support for a gas turbine engine - Google Patents
Front centerbody support for a gas turbine engine Download PDFInfo
- Publication number
- US20120260669A1 US20120260669A1 US13/087,579 US201113087579A US2012260669A1 US 20120260669 A1 US20120260669 A1 US 20120260669A1 US 201113087579 A US201113087579 A US 201113087579A US 2012260669 A1 US2012260669 A1 US 2012260669A1
- Authority
- US
- United States
- Prior art keywords
- front center
- center body
- recited
- section
- support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
- F01D25/164—Flexible supports; Vibration damping means associated with the bearing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/50—Bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/23—Three-dimensional prismatic
- F05D2250/232—Three-dimensional prismatic conical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/40—Transmission of power
- F05D2260/403—Transmission of power through the shape of the drive components
- F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
- F05D2260/40311—Transmission of power through the shape of the drive components as in toothed gearing of the epicyclical, planetary or differential type
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
Definitions
- the present disclosure relates to a gas turbine engine, and in particular, to a case structure therefor.
- Gas turbine engines typically include one or more rotor shafts that transfer power and rotary motion from a turbine section to a compressor section and fan section.
- the rotor shafts are supported within an engine static structure which is typically constructed of modules with individual case sections which are joined together at bolted flanges.
- the flanges form a joint capable of withstanding the variety of loads transmitted through the engine static structure.
- a front center body support for a gas turbine engine includes a front center body section, a bearing section and a frustro-conical interface section about an axis, the frustro-conical interface section between the front center body section and the bearing section.
- a gas turbine engine includes a front center body support defined about an engine longitudinal axis, a centering spring mounted within the front center body support and a flexible support mounted within the front center body support.
- a method for assembling a gas turbine engine according to an exemplary aspect of the present disclosure includes mounting a flexible support within a front center body support.
- FIG. 1 is a schematic cross-section of a gas turbine engine
- FIG. 2 is an enlarged cross-section of a sectional of the gas turbine engine which illustrates a front center body assembly
- FIG. 3 is an enlarged perspective partial cross-section of a front center body support of the front center body assembly.
- FIG. 4 is an enlarged sectional view of the front center body support and flexible support mounted therein.
- FIG. 1 schematically illustrates a gas turbine engine 20 .
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
- Alternative engines might include an augmentor section (not shown) among other systems or features.
- the fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath for compression and communication into the combustor section 26 then expansion through the turbine section 28 .
- FIG. 1 schematically illustrates a gas turbine engine 20 .
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
- Alternative engines might include an augmentor section (not shown) among other systems or features.
- the fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flow
- the engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38 .
- the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42 , a low pressure compressor 44 and a low pressure turbine 46 .
- the inner shaft 40 may drive the fan 42 either directly or through a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30 .
- the high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54 .
- a combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54 .
- the inner shaft 40 and the outer shaft 50 are concentric and rotate about the engine central longitudinal axis A which is collinear with their longitudinal axes.
- Core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52 , mixed with the fuel in the combustor 56 , then expanded over the high pressure turbine 54 and low pressure turbine 46 .
- the turbines 54 , 46 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
- bearing system 38 includes a number two bearing system 38 A located within the compressor section 24 .
- the engine static structure 36 proximate the compressor section 24 includes a front center body assembly 60 .
- the front center body assembly 60 generally includes a front center body support 62 , a seal package 64 , a bearing package 66 of the number two bearing system 38 A, a flex support 68 and a centering spring 70 .
- the flex support 68 is a generally cylindrical structure which provides a flexible attachment of the geared architecture 48 within the front center body support 62 . That is, the flex support 68 reacts the torsional loads from the geared architecture 48 and facilitates vibration absorption as well as other support functions.
- the centering spring 70 is a generally cylindrical cage-like structural component with a multiple of beams which extend between flange end structures.
- the centering spring 70 facilitates a resilient position of the bearing package 66 with respect to the low speed spool 30 .
- the beams are double-tapered beams arrayed circumferentially to control a radial spring rate that may be selected based on a plurality of considerations including, but not limited to, bearing loading, bearing life, rotor dynamics, and rotor deflection considerations.
- the front center body support 62 includes a front center body section 72 and a bearing section 74 defined about axis A with a frustro-conical interface section 76 therebetween.
- the front center body section 72 at least partially defines the core flowpath into the low pressure compressor 44 . That is the front center body section 72 includes an annular passage with a multiple of front center body vanes 72 A, 72 B ( FIG. 3 ).
- the bearing section 74 is defined radially inward of the front center body section 72 .
- the bearing section 74 locates the bearing package 66 and the seal package 64 relative to the low speed spool 30 .
- the frustro-conical interface section 76 combines the front center body section 72 and the bearing section 74 to form a unified load path, free of kinks typical of a conventional flange joint, from the bearing package 66 to the outer periphery of the engine static structure 36 .
- the frustro-conical interface section 76 may include a weld W or, alternatively, be an integral section such that the front center body support 62 is a unitary component.
- the integral, flange-less arrangement of the frustro-conical interface section 76 facilitates a light weight, reduced part count arrangement with an increased ability to tune the overall stiffness to achieve rotor dynamic requirements. Such an arrangement also further integrates functions such as oil and air delivery within the bearing compartment which surrounds bearing package 66 .
- the front center body support 62 also includes mount features to receive the flex support 68 .
- the mount features of the front center body support 62 includes an internal spline 78 and a radial inward directed fastener flange 80 on the front center body section 72 .
- the flex support 68 includes a corresponding outer spline 82 and radially outwardly directed fastener flange 84 .
- the flex support 68 is received into the front center body support 62 at a splined interface 86 formed by splines 78 , 82 and retained therein such that fastener flange 84 abuts fastener flange 80 .
- a set of fasteners 88 such as bolts are then threaded into the fastener flange 80 to mount the flex support 68 within the front center body support 62 .
- the arrangement locates the fasteners 88 to provide access from a forward section of the front center body assembly 60 opposite the bearing package 66 of the number two bearing system 38 A which facilitates assembly and disassembly.
Abstract
Description
- The present disclosure relates to a gas turbine engine, and in particular, to a case structure therefor.
- Gas turbine engines typically include one or more rotor shafts that transfer power and rotary motion from a turbine section to a compressor section and fan section. The rotor shafts are supported within an engine static structure which is typically constructed of modules with individual case sections which are joined together at bolted flanges. The flanges form a joint capable of withstanding the variety of loads transmitted through the engine static structure.
- A front center body support for a gas turbine engine according to an exemplary aspect of the present disclosure includes a front center body section, a bearing section and a frustro-conical interface section about an axis, the frustro-conical interface section between the front center body section and the bearing section.
- A gas turbine engine according to an exemplary aspect of the present disclosure includes a front center body support defined about an engine longitudinal axis, a centering spring mounted within the front center body support and a flexible support mounted within the front center body support.
- A method for assembling a gas turbine engine according to an exemplary aspect of the present disclosure includes mounting a flexible support within a front center body support.
- Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiment. The drawings that accompany the detailed description can be briefly described as follows:
-
FIG. 1 is a schematic cross-section of a gas turbine engine; -
FIG. 2 is an enlarged cross-section of a sectional of the gas turbine engine which illustrates a front center body assembly; -
FIG. 3 is an enlarged perspective partial cross-section of a front center body support of the front center body assembly; and -
FIG. 4 is an enlarged sectional view of the front center body support and flexible support mounted therein. -
FIG. 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. Thefan section 22 drives air along a bypass flowpath while thecompressor section 24 drives air along a core flowpath for compression and communication into thecombustor section 26 then expansion through theturbine section 28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines. - The
engine 20 generally includes alow speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. Thelow speed spool 30 generally includes aninner shaft 40 that interconnects afan 42, alow pressure compressor 44 and alow pressure turbine 46. Theinner shaft 40 may drive thefan 42 either directly or through a gearedarchitecture 48 to drive thefan 42 at a lower speed than thelow speed spool 30. Thehigh speed spool 32 includes anouter shaft 50 that interconnects ahigh pressure compressor 52 andhigh pressure turbine 54. Acombustor 56 is arranged between thehigh pressure compressor 52 and thehigh pressure turbine 54. Theinner shaft 40 and theouter shaft 50 are concentric and rotate about the engine central longitudinal axis A which is collinear with their longitudinal axes. - Core airflow is compressed by the
low pressure compressor 44 then thehigh pressure compressor 52, mixed with the fuel in thecombustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. Theturbines low speed spool 30 andhigh speed spool 32 in response to the expansion. - The
main engine shafts bearing system 38 within thestatic structure 36. In one non-limiting embodiment,bearing system 38 includes a number two bearingsystem 38A located within thecompressor section 24. - With reference to
FIG. 2 , the enginestatic structure 36 proximate thecompressor section 24 includes a frontcenter body assembly 60. The frontcenter body assembly 60 generally includes a frontcenter body support 62, aseal package 64, abearing package 66 of the number two bearingsystem 38A, aflex support 68 and a centeringspring 70. - The
flex support 68 is a generally cylindrical structure which provides a flexible attachment of the gearedarchitecture 48 within the frontcenter body support 62. That is, theflex support 68 reacts the torsional loads from the gearedarchitecture 48 and facilitates vibration absorption as well as other support functions. - The centering
spring 70 is a generally cylindrical cage-like structural component with a multiple of beams which extend between flange end structures. The centeringspring 70 facilitates a resilient position of thebearing package 66 with respect to thelow speed spool 30. In one embodiment, the beams are double-tapered beams arrayed circumferentially to control a radial spring rate that may be selected based on a plurality of considerations including, but not limited to, bearing loading, bearing life, rotor dynamics, and rotor deflection considerations. - The front
center body support 62 includes a frontcenter body section 72 and abearing section 74 defined about axis A with a frustro-conical interface section 76 therebetween. The frontcenter body section 72 at least partially defines the core flowpath into thelow pressure compressor 44. That is the frontcenter body section 72 includes an annular passage with a multiple of frontcenter body vanes FIG. 3 ). - The
bearing section 74 is defined radially inward of the frontcenter body section 72. Thebearing section 74 locates thebearing package 66 and theseal package 64 relative to thelow speed spool 30. - The frustro-
conical interface section 76 combines the frontcenter body section 72 and thebearing section 74 to form a unified load path, free of kinks typical of a conventional flange joint, from thebearing package 66 to the outer periphery of the enginestatic structure 36. The frustro-conical interface section 76 may include a weld W or, alternatively, be an integral section such that the frontcenter body support 62 is a unitary component. The integral, flange-less arrangement of the frustro-conical interface section 76 facilitates a light weight, reduced part count arrangement with an increased ability to tune the overall stiffness to achieve rotor dynamic requirements. Such an arrangement also further integrates functions such as oil and air delivery within the bearing compartment which surrounds bearingpackage 66. - With reference to
FIG. 4 , the frontcenter body support 62 also includes mount features to receive theflex support 68. In one disclosed non-limiting embodiment, the mount features of the frontcenter body support 62 includes aninternal spline 78 and a radial inward directedfastener flange 80 on the frontcenter body section 72. Theflex support 68 includes a correspondingouter spline 82 and radially outwardly directedfastener flange 84. Theflex support 68 is received into the frontcenter body support 62 at asplined interface 86 formed bysplines fastener flange 84abuts fastener flange 80. A set offasteners 88 such as bolts are then threaded into thefastener flange 80 to mount theflex support 68 within the frontcenter body support 62. - The arrangement locates the
fasteners 88 to provide access from a forward section of the frontcenter body assembly 60 opposite thebearing package 66 of the number two bearingsystem 38A which facilitates assembly and disassembly. - It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom.
- Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.
- The foregoing description is exemplary rather than defined by the limitations within. Various non-limiting embodiments are disclosed herein, however, one of ordinary skill in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced other than as specifically described. For that reason the appended claims should be studied to determine true scope and content.
Claims (29)
Priority Applications (10)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/087,579 US20120260669A1 (en) | 2011-04-15 | 2011-04-15 | Front centerbody support for a gas turbine engine |
US13/282,919 US8366385B2 (en) | 2011-04-15 | 2011-10-27 | Gas turbine engine front center body architecture |
US13/407,916 US8360714B2 (en) | 2011-04-15 | 2012-02-29 | Gas turbine engine front center body architecture |
EP12164348.0A EP2511484B1 (en) | 2011-04-15 | 2012-04-16 | Front centerbody support for a gas turbine engine |
US13/732,647 US8911204B2 (en) | 2011-04-15 | 2013-01-02 | Gas turbine engine front center body architecture |
US13/735,100 US8915702B2 (en) | 2011-04-15 | 2013-01-07 | Gas turbine engine front center body architecture |
US13/860,774 US10605167B2 (en) | 2011-04-15 | 2013-04-11 | Gas turbine engine front center body architecture |
US14/325,071 US20140317926A1 (en) | 2011-04-15 | 2014-07-07 | Front centerbody support for a gas turbine engine |
US16/836,001 US11713713B2 (en) | 2011-04-15 | 2020-03-31 | Gas turbine engine front center body architecture |
US18/142,131 US20230272745A1 (en) | 2011-04-15 | 2023-05-02 | Gas turbine engine front center body architecture |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/087,579 US20120260669A1 (en) | 2011-04-15 | 2011-04-15 | Front centerbody support for a gas turbine engine |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US201113275286A Continuation-In-Part | 2011-04-15 | 2011-10-17 |
Related Child Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/282,919 Continuation-In-Part US8366385B2 (en) | 2011-04-15 | 2011-10-27 | Gas turbine engine front center body architecture |
US14/325,071 Division US20140317926A1 (en) | 2011-04-15 | 2014-07-07 | Front centerbody support for a gas turbine engine |
Publications (1)
Publication Number | Publication Date |
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US20120260669A1 true US20120260669A1 (en) | 2012-10-18 |
Family
ID=46022099
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
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US13/087,579 Abandoned US20120260669A1 (en) | 2011-04-15 | 2011-04-15 | Front centerbody support for a gas turbine engine |
US14/325,071 Abandoned US20140317926A1 (en) | 2011-04-15 | 2014-07-07 | Front centerbody support for a gas turbine engine |
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Application Number | Title | Priority Date | Filing Date |
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US14/325,071 Abandoned US20140317926A1 (en) | 2011-04-15 | 2014-07-07 | Front centerbody support for a gas turbine engine |
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US (2) | US20120260669A1 (en) |
EP (1) | EP2511484B1 (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
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JP2013096410A (en) * | 2011-10-27 | 2013-05-20 | United Technologies Corp <Utc> | Gas turbine engine and maintenance method of gas turbine engine |
US20140196471A1 (en) * | 2012-10-01 | 2014-07-17 | United Technologies Corporation | Fan drive gear system flexible support features |
US8911204B2 (en) | 2011-04-15 | 2014-12-16 | United Technologies Corporation | Gas turbine engine front center body architecture |
WO2014197081A3 (en) * | 2013-03-15 | 2015-03-12 | United Technologies Corporation | Integrated flex support and front center body |
US9163522B2 (en) | 2012-08-21 | 2015-10-20 | United Technologies Corporation | Spring carrier and removable seal carrier |
JP2016510101A (en) * | 2013-03-14 | 2016-04-04 | ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation | How to assemble a turbofan engine |
US9695870B2 (en) | 2012-09-25 | 2017-07-04 | United Technologies Corporation | Turbomachine bearing support structure |
US9976443B2 (en) | 2009-11-20 | 2018-05-22 | United Technologies Corporation | Turbofan engine assembly methods |
US20190032571A1 (en) * | 2013-06-06 | 2019-01-31 | United Technologies Corporation | Spline ring for a fan drive gear flexible support |
US10605167B2 (en) | 2011-04-15 | 2020-03-31 | United Technologies Corporation | Gas turbine engine front center body architecture |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2584154B8 (en) * | 2011-10-17 | 2020-10-28 | Raytheon Technologies Corporation | Gas turbine front center body architecture and method of servicing a gas turbine engine |
EP2584153B1 (en) | 2011-10-17 | 2019-01-09 | United Technologies Corporation | Gas turbine engine and method of disassembly |
US10982565B2 (en) | 2013-01-21 | 2021-04-20 | Raytheon Technologies Corporation | Turbine case adjustment using Adjustable tie rods |
US10495004B2 (en) | 2015-09-17 | 2019-12-03 | General Electric Company | Multi-directional gearbox deflection limiter for a gas turbine engine |
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US7926260B2 (en) * | 2006-07-05 | 2011-04-19 | United Technologies Corporation | Flexible shaft for gas turbine engine |
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- 2011-04-15 US US13/087,579 patent/US20120260669A1/en not_active Abandoned
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- 2012-04-16 EP EP12164348.0A patent/EP2511484B1/en active Active
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2014
- 2014-07-07 US US14/325,071 patent/US20140317926A1/en not_active Abandoned
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US20140317926A1 (en) | 2014-10-30 |
EP2511484A2 (en) | 2012-10-17 |
EP2511484B1 (en) | 2019-09-18 |
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